CN115074725A - Repair method for defect of blade edge block of titanium alloy thin blade - Google Patents
Repair method for defect of blade edge block of titanium alloy thin blade Download PDFInfo
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- CN115074725A CN115074725A CN202210753055.4A CN202210753055A CN115074725A CN 115074725 A CN115074725 A CN 115074725A CN 202210753055 A CN202210753055 A CN 202210753055A CN 115074725 A CN115074725 A CN 115074725A
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- 230000007547 defect Effects 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 41
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 28
- 230000008439 repair process Effects 0.000 title claims description 12
- 238000005253 cladding Methods 0.000 claims abstract description 100
- 238000004372 laser cladding Methods 0.000 claims abstract description 26
- 238000007781 pre-processing Methods 0.000 claims abstract description 7
- 230000003746 surface roughness Effects 0.000 claims abstract description 7
- 239000000843 powder Substances 0.000 claims description 26
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 24
- 238000005498 polishing Methods 0.000 claims description 21
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 12
- 229910052786 argon Inorganic materials 0.000 claims description 12
- 229920000742 Cotton Polymers 0.000 claims description 10
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 10
- 239000001301 oxygen Substances 0.000 claims description 10
- 229910052760 oxygen Inorganic materials 0.000 claims description 10
- 229910045601 alloy Inorganic materials 0.000 claims description 8
- 239000000956 alloy Substances 0.000 claims description 8
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 6
- 244000137852 Petrea volubilis Species 0.000 claims description 6
- 239000002932 luster Substances 0.000 claims description 6
- 239000000758 substrate Substances 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims 1
- 238000002844 melting Methods 0.000 claims 1
- 230000008018 melting Effects 0.000 claims 1
- 239000011159 matrix material Substances 0.000 abstract description 10
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000002679 ablation Methods 0.000 abstract description 4
- 230000004927 fusion Effects 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 4
- 230000006378 damage Effects 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 230000005856 abnormality Effects 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
Abstract
The invention discloses a method for repairing a defect of a blade edge block of a titanium alloy thin blade, which belongs to the technical field of laser cladding and comprises the following steps: s1: preprocessing the defects of blade edge blocks of the blades and prefabricating inverted trapezoidal notches; s2: planning a cladding path of the inverted trapezoidal notch and programming; s3: performing laser cladding, wherein the cladding power is adjustable; s4: grinding the cladding surface to the required size and surface roughness; the method solves the technical problems of incomplete fusion, blade edge ablation and matrix deformation easily occurring in the process of repairing the defect of the blade edge block of the thin blade by adopting the conventional laser cladding technology.
Description
Technical Field
The invention belongs to the technical field of laser cladding, and particularly relates to a method for repairing a defect of a blade edge block of a titanium alloy thin blade.
Background
Titanium alloy has become one of the candidate materials for important parts of aero-engine compressor blades, blisks and the like due to the excellent characteristics of high specific strength and good corrosion resistance. The titanium alloy blade has a severe working environment, various damages such as point defects, line defects and block defects can occur in the using process, the point defects and the line defects are mainly concentrated on the surface of the blade generally, and the top end surface of the blade is easy to have the defect of block falling caused by cavitation erosion. If the parts with the defects are directly scrapped, great waste is caused, and various methods for repairing the defects are developed for the parts.
The laser cladding technology can repair damaged parts generated in the production and service processes, three-dimensional growth is carried out on the parts with unqualified sizes, and the geometrical shapes of the parts are recovered by combining later-stage machining. By adopting the laser cladding technology, the surface performance of the material can be improved, and the scrapped unqualified product can be repaired, so that the production cost for replacing new parts is reduced, and the method has wide application prospect in the aviation industry.
When a conventional laser cladding technology is adopted to repair a thin blade with the blade edge thickness of about 1mm, the defect of incomplete fusion easily occurs due to too low laser power, the problem can be solved by increasing the laser power, but the defects of matrix deformation, heat affected zone increase and the like caused by pit formation caused by matrix edge burning are easily caused.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a method for repairing the defects of the blade edge block of the titanium alloy thin blade, so as to solve the technical problems of unfused, blade edge ablation and matrix deformation easily occurring in the process of repairing the defects of the blade edge block of the thin blade by adopting the conventional laser cladding technology.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a repair method for defects of a blade edge block of a titanium alloy thin blade comprises the following steps:
s1: preprocessing the defects of blade edge blocks of the blades and prefabricating inverted trapezoidal notches;
s2: planning a cladding path of the inverted trapezoidal notch and programming;
s3: performing laser cladding, wherein the cladding power is adjustable;
s4: and grinding the cladding surface to the required size and surface roughness.
Preferably, step S1 includes the following steps:
s11: polishing the damaged part of the edge of the blade, and repairing the defect position into an inverted trapezoidal structure;
s12: polishing the damaged part to expose the whole surface of the part to be repaired with metallic luster;
s13: and wiping the surface to be repaired to remove dirt.
Preferably, step S2 includes the following steps:
s21: cladding path inside the trapezoidal notch; the cladding starting point starts from a point A on the bottom edge of the trapezoid, the path is completed by B, C, D, E, F, each cycle consists of three layers of AB, CD and EF, and multiple cycles are carried out until the distance from the last cladding layer to the surface GH of the substrate is within 0.2 mm;
s22: cladding path of the surface of the trapezoid notch; and (3) cladding to the trapezoidal central line by taking the small distance on the left side of the trapezoidal peak G1 as a cladding starting point, cladding to the trapezoidal central line by taking the same distance on the right side of the trapezoidal peak H1 as the cladding starting point, raising the height by a small distance, and repeating the steps once.
Preferably, in step S3, performing laser cladding on the trapezoidal notch by using a laser, where the cladding power inside the trapezoidal notch is 300-320W, the cladding power on the surface of the trapezoidal notch is 220-240W, the cladding rate is 2.6-3.0 mm/S, and the powder feeding speed of the alloy powder is 2.0-2.2 g/min, until the cladding layer fills the trapezoidal notch and is 0.2-0.4 mm higher.
Preferably, in step S11, a polishing knife is used to polish the damaged portion of the blade edge;
in step S12, polishing the damaged part by using P240-mesh sand paper;
in step S13, the surface to be repaired is wiped with absolute ethyl alcohol or acetone and absorbent cotton.
Preferably, in step S21, the cycle number is determined according to the depth h of the cladding gap, and specifically, the cycle number is h/0.9.
Preferably, the laser cladding is performed on the trapezoidal notch by using an IPG laser YLS-1000.
Preferably, the alloy powder is delivered from a powder feeder through a coaxial powder delivery nozzle into the laser melt pool.
Preferably, the entire repair process is carried out in an argon shield box having an oxygen content of less than 5 ppm.
Preferably, the argon flow Q is 4.5-5.5L/min.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a repair method for a defect of a blade edge block of a titanium alloy thin blade.A reverse trapezoidal notch is prefabricated, compared with a common notch, the slope of the reverse trapezoidal notch is more favorable for a molten pool to form metallurgical bonding with a matrix, and the occurrence of defects such as unfused and the like is reduced; planning a cladding path of the inverted trapezoidal notch, and adjusting cladding power according to the planned inverted trapezoidal path and the thickness of the blade edge to obtain better cladding quality and avoid the technical problems of blade edge ablation and matrix deformation; the processing program is compiled according to the planned path, the modular operation and one-key processing can be realized, the operation is convenient, and the quality and the qualification rate of the titanium alloy thin blade repaired by laser cladding are extremely high.
Furthermore, the inside of the inverted trapezoidal notch is repaired by adopting relatively large laser power cladding according to the planned inverted trapezoidal internal path, then the laser power is reduced, and the surface of the defect is repaired by cladding according to the inverted trapezoidal surface path, so that not only can better cladding quality be obtained, but also the technical problems of blade edge ablation and matrix deformation are avoided.
Drawings
FIG. 1 is a schematic diagram of a repair path according to the present invention.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention is described in further detail below with reference to the accompanying drawings:
the invention discloses a method for repairing a defect of a blade edge block of a titanium alloy thin blade, which comprises the following steps:
1) preprocessing the defects of the blade edge blocks of the blades:
a) and polishing the damaged part of the edge of the blade by using a polishing knife, and repairing the defect position into an inverted trapezoidal structure.
b) And (3) polishing the damaged part by using P240-mesh sand paper to expose the whole surface to be repaired of the part with metallic luster.
c) The surface of the cotton wool is wiped by using absolute ethyl alcohol or acetone and absorbent cotton to remove dirt.
2) Performing laser cladding path planning and programming on the inverted trapezoidal notch (see fig. 1):
a) cladding path inside the trapezoidal notch: the starting point of cladding is from a point A at the bottom edge of the trapezoid, the path is B, C, D, E, F to complete a cycle, each cycle is composed of three layers AB, CD and EF, and the thickness of each layer is about 0.3 mm. Determining the cycle times (h/0.9) according to the depth h of the cladding gap until the GH distance between the last cladding layer and the surface of the substrate is within 0.2 mm;
b) cladding path of the surface of the trapezoid notch: cladding to the trapezoidal central line by taking the position 2mm on the left side of the trapezoidal vertex G1 as a cladding starting point, cladding to the trapezoidal central line by taking the position 2mm on the right side of the trapezoidal vertex H1 as a cladding starting point, and repeating the steps once, wherein the height is increased by about 0.2 mm;
3) performing laser cladding by using an IPG laser YLS-1000, wherein the cladding power inside a trapezoid notch is 300-320W, the cladding power on the surface of the trapezoid notch is 220-240W, the cladding speed is 2.6-3.0 mm/s, alloy powder is sent out by a powder feeder and is sent into a laser molten pool through a coaxial powder feeding nozzle, the powder feeding speed is 2.0-2.2 g/min, the whole repairing process is performed in an argon protection box with the oxygen content less than 5ppm, the oxygen absorption and oxidation of titanium alloy in the cladding process are avoided, the argon flow Q is 4.5-5.5L/min, and the cladding layer fills the trapezoid notch and is 0.2-0.4 mm higher so as to leave processing allowance;
4) ground to the required size and surface roughness.
Example 1
First-stage fan blade
The material TC4, the thickness of the blade edge is 0.6-1.2 mm
The damage depth of the blade edge is 5mm, and the width is 8mm
The repairing process comprises the following steps:
1) preprocessing the defects of the blade edge blocks of the blades:
a) and (3) polishing the damaged part of the edge of the blade by adopting a polishing cutter, and repairing the defect position into an inverted trapezoidal structure, wherein the height of the trapezoid is 5.5mm, and the upper edge and the lower edge of the trapezoid are 8mm and 14mm respectively.
b) And (3) polishing the damaged part by using P240-mesh sand paper to expose the whole surface to be repaired of the part with metallic luster.
c) The surface of the cotton wool is wiped by using absolute ethyl alcohol or acetone and absorbent cotton to remove dirt.
2) And (3) carrying out laser cladding path planning on the inverted trapezoidal notch (see the attached drawing):
a) cladding path inside the trapezoidal notch: the starting point of cladding is started from a point A on the bottom edge of the trapezoid, the path is completed by B, C, D, E, F, each cycle is composed of three layers of AB, CD and EF, and the thickness of each layer is 0.3 mm. The depth of the cladding gap is 5.5mm, the determined cycle number is 6, and the GH distance between the last cladding layer and the surface of the substrate is 0.1 mm.
b) Cladding path of the surface of the trapezoid notch: and (3) cladding to the position of the trapezoidal central line by taking the position 2mm on the left side of the trapezoidal vertex G1 as a cladding starting point, cladding to the position of the trapezoidal central line by taking the position 2mm on the right side of the trapezoidal vertex H1 as the cladding starting point, and repeating the steps once when the height is increased by 0.2 mm.
3) Performing laser cladding by using an IPG laser YLS-1000, wherein the cladding power inside a trapezoid notch is 320W, the cladding power on the surface of the trapezoid notch is 240W, the cladding speed is 3.0mm/s, alloy powder is sent out by a powder feeder and is sent into a laser molten pool through a coaxial powder feeding nozzle, the powder feeding speed is 2.2g/min, the whole repairing process is performed in an argon protection box with the oxygen content less than 5ppm, the oxygen absorption and oxidation of titanium alloy in the cladding process are avoided, the argon flow Q is 4.5-5.5L/min, and the cladding layer is filled in the trapezoid notch and is 0.4mm higher so as to leave a processing allowance;
4) ground to the required size and surface roughness.
The detection results are as follows:
a) the metallographic structure analysis result shows that the cladding layer and the matrix form metallurgical bonding;
b) the quality is good without abnormality through X-ray and fluorescence examination;
c) the mechanical property of the titanium alloy after laser cladding reaches more than 90% of the standard of a forged piece;
d) the final size after repair meets the requirements.
Example 2
Second stage blisk blade
The material TC17, the thickness of the blade edge is 0.4-1.1 mm
The damage depth of the blade edge is 3.5mm, and the width is 4mm
The repairing process comprises the following steps:
1) preprocessing the defects of the blade edge blocks of the blades:
a) and (3) polishing the damaged part of the edge of the blade by adopting a polishing cutter, and repairing the defect position into an inverted trapezoidal structure, wherein the height of the trapezoid is 3.8mm, and the upper edge and the lower edge of the trapezoid are respectively 5mm and 10 mm.
b) And (3) polishing the damaged part by using P240-mesh sand paper to expose the whole surface to be repaired of the part with metallic luster.
c) The surface of the cotton wool is wiped by using absolute ethyl alcohol or acetone and absorbent cotton to remove dirt.
2) And (3) carrying out laser cladding path planning on the inverted trapezoidal notch (see the attached drawing):
a) cladding path inside the trapezoidal notch: the starting point of cladding is started from a point A on the bottom edge of the trapezoid, the path is completed by B, C, D, E, F, each cycle is composed of three layers of AB, CD and EF, and the thickness of each layer is 0.3 mm. The depth of the cladding gap is 3.8mm, the determined cycle number is 4, and the GH distance between the last cladding layer and the surface of the substrate is 0.2 mm.
b) Cladding path of the surface of the trapezoid notch: and (3) cladding to the position of the trapezoidal central line by taking the position 2mm on the left side of the trapezoidal vertex G1 as a cladding starting point, cladding to the position of the trapezoidal central line by taking the position 2mm on the right side of the trapezoidal vertex H1 as the cladding starting point, and repeating the steps once when the height is increased by 0.2 mm.
3) Performing laser cladding by using an IPG laser YLS-1000, wherein the cladding power inside a trapezoid notch is 300W, the cladding power on the surface of the trapezoid notch is 220W, the cladding speed is 2.6mm/s, alloy powder is sent out by a powder feeder and is sent into a laser molten pool through a coaxial powder feeding nozzle, the powder feeding speed is 2.0g/min, the whole repairing process is performed in an argon protection box with the oxygen content less than 5ppm, the oxygen absorption and oxidation of titanium alloy in the cladding process are avoided, the argon flow Q is 4.5-5.5L/min, and the cladding layer is filled in the trapezoid notch and is 0.2mm higher so as to leave a processing allowance;
4) ground to the required size and surface roughness.
The detection results are as follows:
a) the metallographic structure analysis result shows that the cladding layer and the matrix form metallurgical bonding;
b) the quality is good without abnormality through X-ray and fluorescence examination;
c) the mechanical property of the titanium alloy after laser cladding reaches more than 90% of the standard of a forged piece;
d) the final size after repair meets the requirements.
Example 3
Third stage blisk blade
The material Ti60, the thickness of the blade edge is 0.3-1.1 mm
The damage depth of the blade edge is 3.5mm, and the width is 4mm
The repairing process comprises the following steps:
1) preprocessing the defects of the blade edge blocks of the blades:
a) and (3) polishing the damaged part of the edge of the blade by adopting a polishing cutter, and repairing the defect position into an inverted trapezoidal structure, wherein the height of the trapezoid is 3.8mm, and the upper edge and the lower edge of the trapezoid are respectively 5mm and 10 mm.
b) And (3) polishing the damaged part by using P240-mesh sand paper to expose the whole surface to be repaired of the part with metallic luster.
c) The surface of the cotton wool is wiped by using absolute ethyl alcohol or acetone and absorbent cotton to remove dirt.
2) And (3) carrying out laser cladding path planning on the inverted trapezoidal notch (see the attached drawing):
a) cladding path inside the trapezoidal notch: the starting point of cladding is started from a point A on the bottom edge of the trapezoid, the path is completed by B, C, D, E, F, each cycle is composed of three layers of AB, CD and EF, and the thickness of each layer is 0.3 mm. The depth of the cladding gap is 3.8mm, the determined cycle number is 4, and the GH distance between the last cladding layer and the surface of the substrate is 0.2 mm.
b) Cladding path of the surface of the trapezoidal notch: and (3) cladding to the position of the trapezoidal central line by taking the position 2mm on the left side of the trapezoidal vertex G1 as a cladding starting point, cladding to the position of the trapezoidal central line by taking the position 2mm on the right side of the trapezoidal vertex H1 as the cladding starting point, and repeating the steps once when the height is increased by 0.2 mm.
3) Performing laser cladding by using an IPG laser YLS-1000, wherein the cladding power inside a trapezoid notch is 310W, the cladding power on the surface of the trapezoid notch is 230W, the cladding speed is 2.8mm/s, alloy powder is sent out by a powder feeder and is sent into a laser molten pool through a coaxial powder feeding nozzle, the powder feeding speed is 2.1g/min, the whole repairing process is performed in an argon protection box with the oxygen content of less than 5ppm, the oxygen absorption and oxidation of titanium alloy in the cladding process are avoided, the argon flow Q is 4.5-5.5L/min, the cladding layer is filled in the trapezoid notch and is 0.3mm higher, so as to leave a processing allowance;
4) ground to the required size and surface roughness.
The detection results are as follows:
a) the metallographic structure analysis result shows that the cladding layer and the matrix form metallurgical bonding;
b) the quality is good without abnormality through X-ray and fluorescence examination;
c) the mechanical property of the titanium alloy after laser cladding reaches more than 90% of the standard of a forged piece;
d) the final size after repair meets the requirements.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (10)
1. A repair method for defects of a blade edge block of a titanium alloy thin blade is characterized by comprising the following steps:
s1: preprocessing the defects of blade edge blocks of the blades and prefabricating inverted trapezoidal notches;
s2: planning a cladding path of the inverted trapezoidal notch and programming;
s3: performing laser cladding, wherein the cladding power is adjustable;
s4: and grinding the cladding surface to the required size and surface roughness.
2. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 1, wherein the step S1 comprises the following steps:
s11: polishing the damaged part of the edge of the blade, and repairing the defect position into an inverted trapezoidal structure;
s12: polishing the damaged part to expose the whole surface of the part to be repaired with metallic luster;
s13: and wiping the surface to be repaired to remove dirt.
3. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 1, wherein the step S2 comprises the following steps:
s21: cladding paths inside the trapezoidal notches; the cladding starting point starts from a point A on the bottom edge of the trapezoid, the path is completed by B, C, D, E, F, each cycle consists of three layers of AB, CD and EF, and multiple cycles are carried out until the distance from the last cladding layer to the surface GH of the substrate is within 0.2 mm;
s22: cladding path of the surface of the trapezoid notch; and (3) cladding to the trapezoidal central line by taking the small distance on the left side of the trapezoidal peak G1 as a cladding starting point, cladding to the trapezoidal central line by taking the same distance on the right side of the trapezoidal peak H1 as the cladding starting point, raising the height by a small distance, and repeating the steps once.
4. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 1, wherein in step S3, a laser is used for laser cladding of the trapezoidal notch, the cladding power inside the trapezoidal notch is 300-320W, the cladding power on the surface of the trapezoidal notch is 220-240W, the cladding rate is 2.6-3.0 mm/S, and the powder feeding speed of the alloy powder is 2.0-2.2 g/min, until the cladding layer fills the trapezoidal notch and is 0.2-0.4 mm higher.
5. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 2, wherein:
in the step S11, polishing the damaged part of the blade edge by a polishing knife;
in step S12, polishing the damaged part by using P240-mesh sand paper;
in step S13, the surface to be repaired is wiped with absolute ethyl alcohol or acetone and absorbent cotton.
6. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 3, wherein in step S21, the cycle number is determined according to the depth h of the cladding notch, and specifically, the cycle number is h/0.9.
7. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 4, wherein an IPG laser YLS-1000 is adopted to carry out laser cladding on the trapezoidal notch.
8. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 4, wherein the alloy powder is sent out by a powder feeder and is sent into a laser melting pool through a coaxial powder feeding nozzle.
9. The method for repairing the defects of the blade edge block of the titanium alloy thin blade as claimed in claim 4, wherein the whole repairing process is carried out in an argon protection box with oxygen content less than 5 ppm.
10. The method for repairing the defect of the blade edge block of the titanium alloy thin blade as claimed in claim 9, wherein the argon gas flow Q is 4.5-5.5L/min.
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| CN114434086A (en) * | 2021-12-26 | 2022-05-06 | 国营四达机械制造公司 | Method for repairing surface cracks of titanium alloy thin-walled workpiece |
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